公开(公告)号：US20190271230A1

公开(公告)日：2019-09-05

申请号：US16003755

申请日：2018-06-08

Applicant: United Technologies Corporation

Inventor： Atul Kohli ,  Jaime G. Ghigliotty ,  James B. Downey

IPC: F01D5/18 ,  F02C3/04

Abstract: An airfoil includes an airfoil body that has a peripheral wall that defines an exterior side and an interior side that bounds an internal cavity in the airfoil body. The peripheral wall has first and second wall sections joined by a transition section. The first wall section is thicker than the second wall section. The transition section provides a change in thickness between the first wall section and the second wall section. The second wall section includes a cooling hole that has a first end that opens to the internal cavity at the interior side and a second end that opens to the exterior side.

公开(公告)号：US10920610B2

公开(公告)日：2021-02-16

申请号：US16004724

申请日：2018-06-11

Applicant: United Technologies Corporation

Inventor： Jaime G. Ghigliotty

IPC: F01D25/12 ,  B22D45/00 ,  F01D9/04

Abstract: A casting plug for a vane of a gas turbine engine includes a plug body a flow control feature and a support that extends between the plug body and the flow control feature.

公开(公告)号：US10436113B2

公开(公告)日：2019-10-08

申请号：US14816125

申请日：2015-08-03

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Thomas N. Slavens ,  Dominic J. Mongillo ,  Steven Bruce Gautschi ,  Jaime G. Ghigliotty

IPC: F01D9/06 ,  F02C7/18 ,  F01D5/08 ,  F01D5/18 ,  F01D5/14 ,  F01D5/30 ,  F02C3/04 ,  F02C9/16

Abstract: A cooling device for a gas turbine engine component comprises a gas turbine engine component having an upstream channel and a downstream channel that define a cooling flow path. A meter feature includes at least one hole to meter flow from the upstream channel to the downstream channel, and has an upstream side and a downstream side. An exit diffuser extends outwardly from the downstream side of the meter feature to control flow in a desired direction into the downstream channel. A gas turbine engine is also disclosed.

公开(公告)号：US20160084164A1

公开(公告)日：2016-03-24

申请号：US14816125

申请日：2015-08-03

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Thomas N. Slavens ,  Dominic J. Mongillo ,  Steven Bruce Gautschi ,  Jaime G. Ghigliotty

IPC: F02C7/18 ,  F02C9/16 ,  F02C3/04

CPC classification number: F02C7/18 ,  F01D5/081 ,  F01D5/145 ,  F01D5/18 ,  F01D5/181 ,  F01D5/182 ,  F01D5/183 ,  F01D5/184 ,  F01D5/185 ,  F01D5/186 ,  F01D5/187 ,  F01D5/188 ,  F01D5/189 ,  F01D5/30 ,  F01D9/06 ,  F01D9/065 ,  F02C3/04 ,  F02C9/16 ,  F05D2220/32 ,  F05D2250/51 ,  F05D2250/71 ,  F05D2250/72 ,  F05D2250/73 ,  F05D2260/232 ,  Y02T50/676

Abstract: A cooling device for a gas turbine engine component comprises a gas turbine engine component having an upstream channel and a downstream channel that define a cooling flow path. A meter feature includes at least one hole to meter flow from the upstream channel to the downstream channel, and has an upstream side and a downstream side. An exit diffuser extends outwardly from the downstream side of the meter feature to control flow in a desired direction into the downstream channel. A gas turbine engine is also disclosed.

Abstract translation: 用于燃气涡轮发动机部件的冷却装置包括具有限定冷却流路的上游通道和下游通道的燃气涡轮发动机部件。 仪表特征包括至少一个孔，用于测量从上游通道到下游通道的流量，并具有上游侧和下游侧。 出口扩散器从仪表特征的下游侧向外延伸以控制在所需方向上的流向下游通道。 还公开了一种燃气涡轮发动机。

公开(公告)号：US10731474B2

公开(公告)日：2020-08-04

申请号：US16003755

申请日：2018-06-08

Applicant: United Technologies Corporation

Inventor： Atul Kohli ,  Jaime G. Ghigliotty ,  James B. Downey

IPC: F01D5/18 ,  F02C3/04 ,  F01D9/04

Abstract: An airfoil includes an airfoil body that has a peripheral wall that defines an exterior side and an interior side that bounds an internal cavity in the airfoil body. The peripheral wall has first and second wall sections joined by a transition section. The first wall section is thicker than the second wall section. The transition section provides a change in thickness between the first wall section and the second wall section. The second wall section includes a cooling hole that has a first end that opens to the internal cavity at the interior side and a second end that opens to the exterior side.

公开(公告)号：US10215031B2

公开(公告)日：2019-02-26

申请号：US14769600

申请日：2014-03-12

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Jaime G. Ghigliotty ,  Edward F. Pietraszkiewicz ,  Dominic J. Mongillo, Jr. ,  Christopher Corcoran

IPC: F01D5/18 ,  B22C9/10 ,  B22D25/02

Abstract: A gas turbine engine component includes first and second walls spaced apart from one another to provide a cooling passage. First and second trip strips are respectively provided on the first and second walls and arranged to face one another. The first and second trip strips are arranged in an interleaved fashion with respect to one another in a direction.

公开(公告)号：US20180038236A1

公开(公告)日：2018-02-08

申请号：US15783741

申请日：2017-10-13

Applicant: United Technologies Corporation

Inventor： Jaime G. Ghigliotty ,  Matthew A. Devore

IPC: F01D9/04 ,  F01D5/18

CPC classification number: F01D9/041 ,  F01D5/189 ,  F05D2220/32 ,  F05D2230/13 ,  F05D2230/14 ,  F05D2240/126 ,  F05D2260/201 ,  F05D2260/202 ,  F05D2260/205 ,  F05D2260/22141 ,  F05D2300/177 ,  Y02T50/676

Abstract: A method of flowing cooling fluid through a stator vane in a gas turbine engine includes the step of providing an airfoil that has an exterior wall that provides a cooling cavity. The exterior surface has an interior surface that has multiple pin fins that extend therefrom. A baffle is arranged in the cooling cavity and supported by the pin fins. A perimeter cavity is provided between the baffle and the exterior wall. The pin fins are arranged in the perimeter cavity. Cooling fluid flows through a region in the perimeter cavity. The pin fins are arranged in the region having a low Reynolds number and through which the cooling fluid

公开(公告)号：US20160003071A1

公开(公告)日：2016-01-07

申请号：US14708830

申请日：2015-05-11

Applicant: United Technologies Corporation

Inventor： Jaime G. Ghigliotty ,  Matthew A. Devore

IPC: F01D9/04

CPC classification number: F01D9/041 ,  F01D5/189 ,  F05D2220/32 ,  F05D2230/13 ,  F05D2230/14 ,  F05D2240/126 ,  F05D2260/201 ,  F05D2260/202 ,  F05D2260/205 ,  F05D2260/22141 ,  F05D2300/177 ,  Y02T50/676

Abstract: A stator vane for a gas turbine engine includes an airfoil that has an exterior wall that provides a cooling cavity. The exterior surface has an interior surface that has multiple pin fins extending therefrom. A baffle is arranged in the cooling cavity and is supported by the pin fins.

Abstract translation: 用于燃气涡轮发动机的定子叶片包括具有提供冷却腔的外壁的翼型件。 外表面具有从其延伸的多个销翅片的内表面。 挡板布置在冷却腔中并由销翅片支撑。

公开(公告)号：US20160003055A1

公开(公告)日：2016-01-07

申请号：US14769600

申请日：2014-03-12

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Jaime G. Ghigliotty ,  Edward F. Pietraszkiewicz ,  Dominic J. Mongillo, JR. ,  Christopher Corcoran

IPC: F01D5/18

CPC classification number: F01D5/186 ,  B22C9/10 ,  B22D25/02 ,  F01D5/187 ,  F05D2220/32 ,  F05D2230/30 ,  F05D2240/303 ,  F05D2240/304 ,  F05D2250/185 ,  F05D2260/202 ,  F05D2260/2212 ,  F05D2260/22141 ,  Y02T50/676

Abstract: A gas turbine engine component includes first and second walls spaced apart from one another to provide a cooling passage. First and second trip strips are respectively provided on the first and second walls and arranged to face one another. The first and second trip strips are arranged in an interleaved fashion with respect to one another in a direction.

Abstract translation: 燃气涡轮发动机部件包括彼此间隔开的第一和第二壁，以提供冷却通道。 第一和第二跳闸带分别设置在第一和第二壁上并且被布置成彼此面对。 第一和第二跳闸带在交叉方式相对于彼此沿一个方向布置。